CN202828100U - Aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlock and deadman - Google Patents
Aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlock and deadman Download PDFInfo
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- CN202828100U CN202828100U CN 201220456344 CN201220456344U CN202828100U CN 202828100 U CN202828100 U CN 202828100U CN 201220456344 CN201220456344 CN 201220456344 CN 201220456344 U CN201220456344 U CN 201220456344U CN 202828100 U CN202828100 U CN 202828100U
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Abstract
The utility model discloses an aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlocks and a deadman. The aircraft fueling device with the interaction control of the aircraft fueling vehicle fueling joint interlocks and the deadman comprises four valve sets. The four valve sets are respectively located in four interlock areas which are connected in parallel, wherein the four interlock areas which are connected in parallel are mutually independent and simultaneously have a complementary function and a multiple interlock function. When the interlocks of an aircraft fueling vehicle fueling joint equipment point and a corresponding aircraft oil inlet cover equipment point are locked, a platform fueling joint circuit interlock electromagnetic control valve and a platform venturi tube conducting electromagnetic control valve are controlled to be ventilated, a platform simulation aircraft box cover electromagnetic control valve is ventilated or a left capstan interlock and a left capstan venture tube conducting electromagnetic control valve are ventilated or a right capstan interlock and a right capstan venture tube conducting electromagnetic control valve are ventilated, a capstan simulation aircraft box cover electromagnetic control valve is ventilated, and aircraft fueling operation can be conducted. When the interlocks of the aircraft fueling vehicle fueling joint equipment point and the corresponding aircraft oil inlet cover equipment point are in unlocking breakdown status, the aircraft fueling operation can not be conducted.
Description
Technical field
The utility model relates to a kind of aircraft refuelling device, is specifically related to the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of a kind of aircraft bowser fueling connection.
Background technology
Aircraft bowser is chain lifting table, spike (the pot type filling car is not installed), ground well joint, lead the ten many places attachment points such as static wire clamp, rear capstan winch fueling connection, lifting table fueling connection, aircraft oil case lid and be installed in series.
Stop to the refueling position of aircraft when aircraft bowser, oiling person implements the dead work of refueling operation, after above-mentioned any one equipment point action, and the chain locking-in state that just is in of this aircraft bowser.
When aircraft bowser chain was in locking-in state, aircraft bowser was discharged the air pressure in the trailing wheel compressed air brake cylinder simultaneously owing to hanging not advance the gear of change-speed box and can not travel, and reached brake action (benz car for without pneumatic brake).When any one of aircraft bowser is chain when being in locking-in state, gas path control valve is opened, and total source of the gas air pressure changes benchmark air pressure (about 0.45MPa) into through pressure maintaining valve and arrives electromagnetic valve upstream by the slow-witted graceful control of moral.
After fueling connection (capstan winch fueling connection or lifting table fueling connection) was connected to aircraft and is subjected to hydraulic fluid port, the PCV (Pressure Control Valve, overpressure control cock) that the Venturi tube on this filling conduit leads to valve of underground well was opened; Venturi tube feedback pressure (simulation fueling connection terminal pressure) participates in the aperture of adjusting PCV valve, namely controls the flow velocity of aircraft refuelling;
The ground well joint be connected with ground well and other refueling operation dead work ready after, oiling person presses that slow-witted moral is graceful, the reference gas pressure electromagnetic valve is opened, reference gas is pressed onto the air chamber that reaches valve of underground well and opens PCV, the operation of beginning aircraft refuelling;
After the aircraft refuelling end of job, oiling person all playbacks fueling connection, ground well joint and other equipment; Make the chain released state (removing partner's locking of brake and releasing change speed gear box) that all is in of filling car, filling car is withdrawn the aircraft refuelling position.
There is following defective in the method for the chain control refueling operation of existing aircraft bowser:
1, each equipment point of aircraft bowser installation interlocks in and is difficult for when checking being found intuitively fault; This be since each aircraft bowser that 10 many places equipment points all are installed is chain, not only loaded down with trivial details but also consuming time for the inspection that equipment point is chain, if the supervisory personnel is undetected or careless during chain inspection, the chain fault of aircraft bowser is not in time found, can cause very serious potential safety hazard;
If the chain released state fault that is in of 2 platform fueling connection equipment points or capstan winch fueling connection equipment point, the oil circuit that Venturi tube leads to valve of underground well PCV grease chamber on this filling conduit during refueling operation is not opened, the Venturi tube feedback pressure can not be simulated the aperture that the fueling connection terminal pressure participates in regulating PCV, and this moment, PCV was in full-gear; The aircraft refuelling flow velocity is in maxim, considerably beyond the restriction of " aerocraft oil plant system can accept to be equivalent to the oil plant flow velocity of 3.5bar (50lbf/in) maximum pressure ", exists wrap up to be subjected to the serious hidden danger of oil system;
If the chain released state fault that is in of 3 platform fueling connection equipment points or capstan winch fueling connection equipment point, and refueling operation finishes rear oiling person because responsibility is not operated against regulations by force or misoperation, (miscellaneous equipment is put chain whole release) do not pulled down the fueling connection filling car that just drives an airplane and sailed out of the aircraft refuelling position after miscellaneous equipment playback, can draw flying coffin to be subjected to the dangerous accident of hydraulic fluid port, and draw flying coffin happened occasionally by the dangerous accident of hydraulic fluid port at home and abroad;
4, because the chain of each equipment point of aircraft bowser is to be installed in series; Be in like logical with like non-logical mechanical breakdown the time when any one equipment point is chain, be positioned at the chain then cisco unity malfunction of each equipment point at this equipment point rear;
5, because the chain of each equipment point of aircraft bowser is to be installed in series, and each equipment point interlocking signal is aggregated into an overhead control valve and implements control, this control cock control benchmark air pressure, the chain braking of aircraft bowser, aircraft bowser change-speed box gear locking, when this control cock fault, can not implement the aircraft refuelling operation, and the chain whole inefficacies of aircraft bowser.
The utility model content
Technical problem to be solved in the utility model provides the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of a kind of aircraft bowser fueling connection, and it can prevent from drawing flying coffin to be subjected to the dangerous accident of hydraulic fluid port.
For solving the problems of the technologies described above, the technical solution of the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of the utility model aircraft bowser fueling connection is:
Comprise the urgent flame-out Pneumatic valve 11 that stops to refuel for the control emergency flameout device, the urgent flame-out exit end that stops to refuel Pneumatic valve 11 connects by main gas circuit pipeline stays the graceful benchmark air pressure of moral, the urgent flame-out arrival end that stops to refuel Pneumatic valve 11 is by gas circuit pipeline connecting platform simulated aircraft lid solenoid electric valve 12, and platform simulation aircraft lid solenoid electric valve 12 connects two branch roads parallel with one another by gas circuit pipeline; Be provided with on the first branch road and be in series with the first shuttle valve 15 and the chain Pneumatic valve 14 of gas circuit on chain solenoid electric valve 13, the second branch roads of platform fueling connection circuit; Two branch roads connect source of the gas 10 by the first gas circuit pipeline, simultaneously by the second gas circuit pipeline connecting platform Venturi tube conducting solenoid electric valve 16, and platform Venturi tube conducting solenoid electric valve 16 connecting platform Venturi tube Pneumatic valves 17; The chain Pneumatic valve 14 of gas circuit connects the lock solenoid electric valve 18 that is electrically connected by gas circuit pipeline L6; The first shuttle valve 15 connects the vehicle linkage point; The first shuttle valve 15 connects two parallel branches by another gas circuit pipeline, is provided with capstan winch simulated aircraft lid solenoid electric valve 21 on the first parallel branch, and capstan winch simulated aircraft lid solenoid electric valve 21 flame-outly stops to refuel Pneumatic valve 11 and is connected in series with urgent; The first exit end that the second parallel branch connects the second shuttle valve 22, the second shuttle valves 22 connects respectively the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24, right capstan winch Venturi tube Pneumatic valve 23 by gas circuit pipeline; The second exit end of the second shuttle valve 22 connects respectively the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26, left capstan winch Venturi tube Pneumatic valve 25 by gas circuit pipeline; After merging, the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 place branch roads and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26 place branch roads pass through gas circuit pipeline connecting platform and capstan winch cross complaint solenoid electric valve 27; Platform is connected source of the gas 10 with capstan winch cross complaint solenoid electric valve 27 by gas circuit pipeline; First group of valve, namely the chain solenoid electric valve 13 of platform fueling connection circuit and platform Venturi tube conducting solenoid electric valve 16 are chain for the platform fueling connection equipment point in the chain district of control platform fueling connection electric signal; Second group of valve, namely chain the and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26 are chain for the capstan winch fueling connection equipment point in the chain district of control capstan winch fueling connection electric signal; The 3rd group of valve, the i.e. chain Pneumatic valve of gas circuit 14 pneumatic-electric signal that is used for the equipment points such as the control ground well joint folding and unfolding chain district that combines; The 4th group of valve, the lock solenoid electric valve 18 that namely is electrically connected are used for the control aircraft and are subjected to oil port cover and indivedual chain district of electrostatic conductor electric signal; Above four groups of valves are in respectively four desmic regions in parallel, and four zones that are connected in parallel are separate, can play simultaneously complementary and multiple chain effect.
When the chain and corresponding aircraft of aircraft bowser fueling connection equipment point be subjected to oil port cover equipment point interlock in locking-in state the time, control the chain solenoid electric valve 13 of described platform fueling connection circuit and 16 ventilations of platform Venturi tube conducting solenoid electric valve, 12 ventilations of platform simulation aircraft lid solenoid electric valve or 26 ventilations of the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve or 24 ventilations of the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve, 21 ventilations of capstan winch simulated aircraft lid solenoid electric valve just can be carried out the aircraft refuelling operation; When being subjected to oil port cover equipment point to interlock in the release faulty condition, the chain or corresponding aircraft of aircraft bowser fueling connection equipment point just can't carry out refueling operation.
The chain solenoid electric valve 13 of described platform fueling connection circuit and platform Venturi tube conducting solenoid electric valve 16 are by same Control.
Describedly urgent flame-out stop to refuel Pneumatic valve 11 and be normally open valve.
The technique effect that the utility model can reach is:
1, when platform fueling connection or capstan winch fueling connection and the chain locking-in state that is in of its fueling connection equipment point after aircraft is connected by hydraulic fluid port, the Venturi tube feedback control valve on the corresponding filling conduit just is opened;
2, fueling connection is with after aircraft is connected by hydraulic fluid port, the chain locking-in state that is in of fueling connection equipment point, corresponding aircraft is subjected to the chain box of oil port cover also must place the aircraft oil case lid, its chain locking-in state that is in, and the slow-witted graceful benchmark air pressure of moral can arrive the electromagnetic valve upstream of the slow-witted graceful control of moral;
3, the Venturi tube feedback pressure control cock source of the gas on the chain and capstan winch filling conduit of platform fueling connection cover plate is chain when being in locking-in state corresponding two-position three way magnetic valve control capstan winch fueling connection equipment point is not subjected to the impact of the breakdown of equipment of capstan winch filling conduit or maloperation during the platform oiling;
4, complementary and multiple chain effect: when aircraft bowser is implemented refueling operation, when some cascading failures and chain corresponding control cock fault, need only the chain and corresponding control cock of platform fueling connection or capstan winch fueling connection equipment point working properly, aircraft bowser is chain still to be in locking-in state; Aircraft bowser can be implemented the aircraft refuelling operation;
5, platform fueling connection, the playback of capstan winch fueling connection are confirmed; Oiling person is after having confirmed the playback of aircraft bowser fueling connection, must be by lower platform fueling connection, capstan winch fueling connection playback acknowledge button and when each equipment interlocking of aircraft bowser all is in released state, the filling car that can drive an airplane sails out of the aircraft refuelling position.
Description of drawings
Below in conjunction with the drawings and specific embodiments the utility model is described in further detail:
Fig. 1 is the schematic diagram that the platform of the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of the utility model aircraft bowser fueling connection refuels;
Fig. 2 is the schematic diagram that capstan winch of the present utility model refuels.
Description of reference numerals among the figure:
11 are the urgent flame-out Pneumatic valve (two-position three-way) that stops to refuel,
12 is platform simulation aircraft lid solenoid electric valve (two-position three way magnetic valve),
13 is the chain solenoid electric valve of platform fueling connection circuit (two-position three way magnetic valve),
14 is the chain Pneumatic valve of gas circuit (two-position three-way),
15 is the first shuttle valve,
16 is platform Venturi tube conducting solenoid electric valve (two-position three way magnetic valve),
17 is platform Venturi tube Pneumatic valve (two-position),
18 are the lock solenoid electric valve (two-position three way magnetic valve) that is electrically connected,
21 is capstan winch simulated aircraft lid solenoid electric valve (two-position three way magnetic valve),
22 is the second shuttle valve,
23 is right capstan winch Venturi tube Pneumatic valve (two-position),
24 is the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve (two-position three way magnetic valve),
25 is left capstan winch Venturi tube Pneumatic valve (two-position),
26 is the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve (two-position three way magnetic valve),
27 is platform and capstan winch cross complaint solenoid electric valve (two-position three way magnetic valve),
10 is source of the gas.
The specific embodiment
As shown in Figure 1, the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of the utility model aircraft bowser fueling connection, comprise the urgent flame-out Pneumatic valve 11 that stops to refuel for the control emergency flameout device, the urgent flame-out exit end that stops to refuel Pneumatic valve 11 connects by main gas circuit pipeline L1 stays the graceful benchmark air pressure of moral, the urgent flame-out arrival end that stops to refuel Pneumatic valve 11 is by gas circuit pipeline L2 connecting platform simulated aircraft lid solenoid electric valve 12, and platform simulation aircraft lid solenoid electric valve 12 connects two branch road L4, L5 parallel with one another by gas circuit pipeline L3;
Be provided with on the first branch road L4 on chain solenoid electric valve 13, the second branch road L5 of platform fueling connection circuit and be in series with the first shuttle valve 15 and the chain Pneumatic valve 14 of gas circuit;
Two branch road L4, L5 connect source of the gas 10 by the first gas circuit pipeline L7, simultaneously by the second gas circuit pipeline L8 connecting platform Venturi tube conducting solenoid electric valve 16, and platform Venturi tube conducting solenoid electric valve 16 connecting platform Venturi tube Pneumatic valves 17;
The chain Pneumatic valve 14 of gas circuit connects the lock solenoid electric valve 18 that is electrically connected by gas circuit pipeline L6;
The first shuttle valve 15 connects the vehicle linkage point;
Urgent flame-out stop to refuel Pneumatic valve 11 and be normally open valve;
The chain solenoid electric valve 13 of platform fueling connection circuit and platform Venturi tube conducting solenoid electric valve 16 are by same Control; Other solenoid electric valve is controlled respectively by relay separately;
As shown in Figure 2, the first shuttle valve 15 connects two parallel branches by another gas circuit pipeline L9, be provided with capstan winch simulated aircraft lid solenoid electric valve 21 on the first parallel branch L10, capstan winch simulated aircraft lid solenoid electric valve 21 flame-outly stops to refuel Pneumatic valve 11 and is connected in series with urgent;
The first exit end that the second parallel branch L11 connects the second shuttle valve 22, the second shuttle valves 22 connects respectively the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24, right capstan winch Venturi tube Pneumatic valve 23 by gas circuit pipeline L12; The second exit end of the second shuttle valve 22 connects respectively the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26, left capstan winch Venturi tube Pneumatic valve 25 by gas circuit pipeline L13;
After merging, the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 place branch roads and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26 place branch roads pass through gas circuit pipeline L14 connecting platform and capstan winch cross complaint solenoid electric valve 27;
Platform and capstan winch cross complaint solenoid electric valve 27 are connected source of the gas 10 by gas circuit pipeline L15;
Wherein, first group of valve, namely the chain solenoid electric valve 13 of platform fueling connection circuit and platform Venturi tube conducting solenoid electric valve 16 are chain for the platform fueling connection equipment point in the chain district of control platform fueling connection electric signal;
Second group of valve, namely chain the and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26 are chain for the capstan winch fueling connection equipment point in the chain district of control capstan winch fueling connection electric signal;
The 3rd group of valve, namely the chain Pneumatic valve of gas circuit 14 pneumatic-electric signal that is used for the equipment points such as the control ground well joint folding and unfolding chain district that combines comprises and leads static line (gas), the right side in refuelling platform, left spike, a left side to lead the equipment point such as static line (gas) chain;
The 4th group of valve, the lock solenoid electric valve 18 that namely is electrically connected are used for the control aircraft and comprised by oil port cover and indivedual chain districts of electrostatic conductor electric signal to be subjected to oil port cover, ground well pallet, right spike, a left side to lead static line (electricity), the right side by aircraft that to lead the equipment point such as static line (electricity) chain;
Above four groups of valves are in respectively four desmic regions in parallel (equipment point, the aircrafts such as platform fueling connection, capstan winch fueling connection, the folding and unfolding of ground well joint are subjected to the chain of oil port cover and indivedual electrostatic conductors), four zones that are connected in parallel are separate, can play simultaneously complementary and multiple chain effect.
When the chain and corresponding aircraft of aircraft bowser fueling connection equipment point be subjected to oil port cover equipment point interlock in locking-in state the time, the control platform chain solenoid electric valve 13 of fueling connection circuit and 16 ventilations of platform Venturi tube conducting solenoid electric valve, 12 ventilations of platform simulation aircraft lid solenoid electric valve or 26 ventilations of the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve (also can be 24 ventilations of the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve), 21 ventilations of capstan winch simulated aircraft lid solenoid electric valve just can be carried out the aircraft refuelling operation;
When being subjected to oil port cover equipment point to interlock in the release faulty condition, the chain or corresponding aircraft of aircraft bowser fueling connection equipment point just can't carry out refueling operation, oiling person just can find in time that fueling connection or corresponding aircraft are subjected to oil port cover chainly has a release fault, remedy aircraft bowser and originally needed only any one linkage point at locking-in state, even fueling connection interlocks in the great technological deficiency that released state also can carry out refueling operation, greatly improved the safety that aircraft refuelling work, aircraft are subjected to oil system.
Principle of work of the present utility model is as follows:
One, implementing platform refuels:
Connect lead the static line, prop spike, connect ground well after, make chain Pneumatic valve 14 ventilations of gas circuit, the chain locking-in state that is in; Perhaps, the lock solenoid electric valve 18 that is electrically connected is died, and controls simultaneously chain Pneumatic valve 14 ventilations of gas circuit, the chain locking-in state that is in;
When chain Pneumatic valve 14 ventilations of gas circuit, chain when being in locking-in state, only control chain braking and aircraft bowser change-speed box gear locking, air pressure can be by the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful benchmark air pressure of moral (about 0.45MPa) can't arrive the electromagnetic valve upstream by the slow-witted graceful control of moral, oiling person operates the PCV air chamber that slow-witted De Manshiyin benchmark air pressure does not arrive the ground well joint, and ground well joint PCV can not be opened and namely can't implement refueling operation;
After platform fueling connection cover plate is in locking-in state, platform and capstan winch cross complaint solenoid electric valve 27 are died, cut off the Venturi tube feedback pressure control cock source of the gas on the chain and capstan winch filling conduit of capstan winch fueling connection equipment point, be not subjected to the impact of the breakdown of equipment of capstan winch filling conduit or maloperation during the platform oiling;
After platform fueling connection and aircraft are connected by hydraulic fluid port, the chain solenoid electric valve 13 of platform fueling connection circuit and 16 ventilations of platform Venturi tube conducting solenoid electric valve, air pressure one tunnel arrives chain brake and aircraft bowser change-speed box gear locking, one the tunnel arrives platform simulation aircraft lid solenoid electric valve 12 upstreams, platform simulation aircraft lid solenoid electric valve 12 is in closed condition at this moment, so air pressure still can be by the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful benchmark air pressure of moral can't arrive the electromagnetic valve upstream by the slow-witted graceful control of moral, still can't refuel; Only have and be subjected to oil port cover to put into the chain box of platform fuel lid in aircraft, one road power supply signal is given the lock solenoid electric valve 18 that is electrically connected, another road power supply signal is to platform simulation aircraft lid solenoid electric valve 12, make platform simulation aircraft lid solenoid electric valve 12 be in channel status, Pneumatic pipe cleaner is crossed the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful reference gas of moral is pressed onto the electromagnetic valve upstream that reaches by the slow-witted graceful control of moral, and oiling person pins to stay and just can normally refuel after graceful;
If left spike, a left side were led static line (gas), the right side and were led static line (gas) ground well pallet, right spike, the right side and lead static line (electricity) linkage point fault this moment, cause the chain Pneumatic valve 14 of gas circuit can not control the chain locking-in state that is in, because the chain solenoid electric valve 13 of platform fueling connection circuit and platform Venturi tube conducting solenoid electric valve 16 are installed in parallel with the chain Pneumatic valve 14 of gas circuit, still make its chain locking-in state that is in;
If the chain solenoid electric valve 13 of platform fueling connection circuit of platform fueling connection equipment point and platform Venturi tube conducting solenoid electric valve 16, platform are subjected to oil port cover equipment point chain, or during platform simulation aircraft lid solenoid electric valve 12 some et out of orders, out of reach complementation and multiple chain effect, then can't implement refueling operation, surmount oiling any one chain slow-witted moral when being in that oiling person can implement emergency rating in the locking-in state is graceful this moment.
Two, implementing capstan winch refuels:
When left (right side) capstan winch joint refuels, connect lead the static line, prop spike, connect ground well after, by chain Pneumatic valve 14 ventilations of gas circuit, the chain locking-in state that is in; The lock solenoid electric valve 18 that perhaps is electrically connected is died, and controls simultaneously chain Pneumatic valve 14 ventilations of gas circuit, the chain locking-in state that is in;
When chain Pneumatic valve 14 ventilations of gas circuit, chain when being in locking-in state, only control chain brake and aircraft bowser change-speed box gear locking, air pressure can be by the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful benchmark air pressure of moral (about 0.45MPa) can't arrive the electromagnetic valve upstream by the slow-witted graceful control of moral, can't implement refueling operation;
At left (right side) capstan winch fueling connection with after aircraft is connected by hydraulic fluid port, chain and the right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 or 26 ventilations of the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve, air pressure one tunnel arrives aircraft bowser braking and aircraft bowser Transmission gear locking, another road arrives capstan winch simulated aircraft lid solenoid electric valve 21 upstreams, be in closed condition because of capstan winch simulated aircraft lid solenoid electric valve 21 this moment, so air pressure can be by the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful benchmark air pressure of moral can't arrive the electromagnetic valve upstream by the slow-witted graceful control of moral, can't implement refueling operation;
Only have after capstan winch fueling connection aircraft is subjected to put into fuel lid in the hydraulic fluid port hamper, one road power supply signal is given the lock solenoid electric valve 18 that is electrically connected, another road power supply signal is to capstan winch simulated aircraft lid solenoid electric valve 21, make capstan winch simulated aircraft lid solenoid electric valve 21 be in channel status, Pneumatic pipe cleaner is crossed the urgent flame-out main gas circuit pipeline L1 of Pneumatic valve 11 arrival that stops to refuel, the slow-witted graceful reference gas of moral is pressed onto the electromagnetic valve upstream that reaches by the slow-witted graceful control of moral, and oiling person pins to stay and just can normally refuel after graceful;
If left spike, a left side are led static line (gas), the right side and are led that static line (gas), ground well pallet, right spike, a left side are led static line (electricity), static line (electricity) equipment point cascading failure is led on the right side, cause the chain Pneumatic valve 14 of gas circuit can not control the chain locking-in state effect that is in, because the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve 24 and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26 are installed in parallel with the chain Pneumatic valve 14 of gas circuit respectively, still make its chain locking-in state that is in; When if the chain and right capstan winch Venturi tube of the right capstan winch conducting solenoid electric valve 24 that capstan winch fueling connection equipment point is chain or the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve 26, capstan winch fueling connection are subjected to the chain or capstan winch simulated aircraft lid solenoid electric valve 21 some et out of orders of oil port cover equipment point, out of reach complementation and multiple chain effect, then can't implement refueling operation, surmount oiling any one chain slow-witted moral when being in that oiling person can implement emergency rating in the locking-in state is graceful this moment.
Claims (3)
1. the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of aircraft bowser fueling connection, it is characterized in that: comprise the urgent flame-out Pneumatic valve (11) that stops to refuel for the control emergency flameout device, the urgent flame-out exit end that stops to refuel Pneumatic valve (11) connects by main gas circuit pipeline stays the graceful benchmark air pressure of moral, the urgent flame-out arrival end that stops to refuel Pneumatic valve (11) is by gas circuit pipeline connecting platform simulated aircraft lid solenoid electric valve (12), and platform simulation aircraft lid solenoid electric valve (12) connects two branch roads parallel with one another by gas circuit pipeline;
Be provided with the chain solenoid electric valve of platform fueling connection circuit (13) on the first branch road, be in series with the first shuttle valve (15) and the chain Pneumatic valve of gas circuit (14) on the second branch road;
Two branch roads connect source of the gas (10) by the first gas circuit pipeline, pass through simultaneously the second gas circuit pipeline connecting platform Venturi tube conducting solenoid electric valve (16), platform Venturi tube conducting solenoid electric valve (16) connecting platform Venturi tube Pneumatic valve (17);
The chain Pneumatic valve of gas circuit (14) connects the lock solenoid electric valve (18) that is electrically connected by gas circuit pipeline;
The first shuttle valve (15) connects the vehicle linkage point;
The first shuttle valve (15) connects two parallel branches by another gas circuit pipeline, be provided with capstan winch simulated aircraft lid solenoid electric valve (21) on the first parallel branch, capstan winch simulated aircraft lid solenoid electric valve (21) stops to refuel Pneumatic valve (11) and is connected in series with urgent flame-out;
The second parallel branch connects the second shuttle valve (22), and the first exit end of the second shuttle valve (22) connects respectively the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve (24), right capstan winch Venturi tube Pneumatic valve (23) by gas circuit pipeline; The second exit end of the second shuttle valve (22) connects respectively the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve (26), left capstan winch Venturi tube Pneumatic valve (25) by gas circuit pipeline;
After merging, the chain and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve (24) place branch road and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve (26) place branch road pass through gas circuit pipeline connecting platform and capstan winch cross complaint solenoid electric valve (27);
Platform is connected source of the gas (10) with capstan winch cross complaint solenoid electric valve (27) by gas circuit pipeline;
First group of valve, namely the chain solenoid electric valve of platform fueling connection circuit (13) and platform Venturi tube conducting solenoid electric valve (16) are chain for the platform fueling connection equipment point in the chain district of control platform fueling connection electric signal;
Second group of valve, namely chain the and right capstan winch Venturi tube of right capstan winch conducting solenoid electric valve (24) and the chain and left capstan winch Venturi tube of left capstan winch conducting solenoid electric valve (26) are chain for the capstan winch fueling connection equipment point in the chain district of control capstan winch fueling connection electric signal;
The 3rd group of valve, the i.e. chain Pneumatic valve of gas circuit (14) pneumatic-electric signal that is used for the equipment points such as the control ground well joint folding and unfolding chain district that combines;
The 4th group of valve, the lock solenoid electric valve (18) that namely is electrically connected are used for the control aircraft and are subjected to oil port cover and indivedual chain district of electrostatic conductor electric signal;
Above four groups of valves are in respectively four desmic regions in parallel, and four zones that are connected in parallel are separate, can play simultaneously complementary and multiple chain effect.
2. the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of aircraft bowser fueling connection according to claim 1 is characterized in that: the described chain solenoid electric valve of platform fueling connection circuit (13) and platform Venturi tube conducting solenoid electric valve (16) are by same Control.
3. the aircraft refuelling device of the graceful cross complaint of the chain and slow-witted moral of aircraft bowser fueling connection according to claim 1 is characterized in that: described urgent flame-out to stop to refuel Pneumatic valve (11) be normally open valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220456344 CN202828100U (en) | 2012-09-07 | 2012-09-07 | Aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlock and deadman |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220456344 CN202828100U (en) | 2012-09-07 | 2012-09-07 | Aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlock and deadman |
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| CN202828100U true CN202828100U (en) | 2013-03-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201220456344 Withdrawn - After Issue CN202828100U (en) | 2012-09-07 | 2012-09-07 | Aircraft fueling device with interaction control of aircraft fueling vehicle fueling joint interlock and deadman |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662073A (en) * | 2012-09-07 | 2014-03-26 | 上海浦东国际机场航空油料有限责任公司 | Aircraft refueling device with refueling joint chain of aircraft refueling vehicle and deadman controlled mutually |
| CN106477066A (en) * | 2016-06-08 | 2017-03-08 | 航天晨光股份有限公司 | A kind of aircraft bowser being equipped with automatic transmission |
| CN108773498A (en) * | 2018-07-24 | 2018-11-09 | 汽（四川）专用汽车有限公司 | The device put is interlocked for fixing gravity oiling rifle and detecting safe parking |
| CN108974386A (en) * | 2018-07-24 | 2018-12-11 | 汽（四川）专用汽车有限公司 | Refuel the device for connecing mouth and detecting safe parking interlocking point for fixation pressure |
| CN114488771A (en) * | 2022-01-27 | 2022-05-13 | 中国商用飞机有限责任公司 | Emergency oil drainage comprehensive control system |
-
2012
- 2012-09-07 CN CN 201220456344 patent/CN202828100U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662073A (en) * | 2012-09-07 | 2014-03-26 | 上海浦东国际机场航空油料有限责任公司 | Aircraft refueling device with refueling joint chain of aircraft refueling vehicle and deadman controlled mutually |
| CN103662073B (en) * | 2012-09-07 | 2015-12-09 | 上海浦东国际机场航空油料有限责任公司 | The aircraft refuelling device of the chain and graceful cross complaint of slow-witted moral of aircraft bowser fueling connection |
| CN106477066A (en) * | 2016-06-08 | 2017-03-08 | 航天晨光股份有限公司 | A kind of aircraft bowser being equipped with automatic transmission |
| CN106477066B (en) * | 2016-06-08 | 2019-01-04 | 航天晨光股份有限公司 | A kind of aircraft bowser being equipped with automatic transmission |
| CN108773498A (en) * | 2018-07-24 | 2018-11-09 | 汽（四川）专用汽车有限公司 | The device put is interlocked for fixing gravity oiling rifle and detecting safe parking |
| CN108974386A (en) * | 2018-07-24 | 2018-12-11 | 汽（四川）专用汽车有限公司 | Refuel the device for connecing mouth and detecting safe parking interlocking point for fixation pressure |
| CN114488771A (en) * | 2022-01-27 | 2022-05-13 | 中国商用飞机有限责任公司 | Emergency oil drainage comprehensive control system |
| CN114488771B (en) * | 2022-01-27 | 2024-02-20 | 中国商用飞机有限责任公司 | Emergency oil drain integrated control system |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20130327 Effective date of abandoning: 20151209 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |